EP0188823B1 - Abschlussvorrichtung für eine Flügelfläche - Google Patents

Abschlussvorrichtung für eine Flügelfläche Download PDF

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Publication number
EP0188823B1
EP0188823B1 EP85201286A EP85201286A EP0188823B1 EP 0188823 B1 EP0188823 B1 EP 0188823B1 EP 85201286 A EP85201286 A EP 85201286A EP 85201286 A EP85201286 A EP 85201286A EP 0188823 B1 EP0188823 B1 EP 0188823B1
Authority
EP
European Patent Office
Prior art keywords
door
airfoil
leading edge
opening
connecting member
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
EP85201286A
Other languages
English (en)
French (fr)
Other versions
EP0188823A1 (de
Inventor
James W. Pace
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Boeing Co
Original Assignee
Boeing Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Boeing Co filed Critical Boeing Co
Publication of EP0188823A1 publication Critical patent/EP0188823A1/de
Application granted granted Critical
Publication of EP0188823B1 publication Critical patent/EP0188823B1/de
Expired legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
    • B64C9/22—Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing

Definitions

  • the invention relates to an airfoil as defined in the introductory part of claim 1.
  • Aircraft wings are commonly designed with leading edge flaps or slats which have a retracted position for cruise, and a downwardly and forwardly extended position for high lift operation, such as in takeoff and landing.
  • the flaps or slats In the cruise configuration, the flaps or slats generally conceal the main or fixed leading edge structure of the airfoil, but in the deployed position, the surface of this leading edge structure of the airfoil is exposed to airflow, in circumstances where, for example, the flap or slat forms with the main leading edge structure a slot for flow of air therethrough.
  • connecting member extending between the flap and the wing structure, such as a track which supports the flap, or a servicing member such as a telescopic thermal anti-icing duct.
  • interconnecting members In some circumstances, it is necessary for these interconnecting members to penetrate (i.e. extend) through the skin forming the leading edge surface of the main airfoil structure.
  • An airfoil structure of this kind is known from GB-A-I 572 004.
  • the means for closing the opening are formed by an annular seal of resilient material.
  • the invention has for its object to provide an airfoil of the kind set forth above, in which the opening formed in the front skin section can adequately be closed, specifically when the connecting member has a component of motion in said opening generally transverse to the chord- wise axis.
  • the track 18 is formed in a moderate curve. Further, the forward end 24 of the track 18 extends moderately upwardly from the forward portion of the main curved portion of the track 18. With this particular arrangement, as the track 18 moves from the position of Figure 1 to the positions of Figure 2, the motion of the track is such that the track 18 has not only a forward but a downward component of motion in a vertical plane generally parallel to the cordwise axis of the wing 10.
  • the opening 42 can be considered as having a forward opening portion 42a which curves from a lower location upwardly past the forwardmost portion of the forward skin portion 38 and upwardly therefrom a short distance in the upwardly and rearwardly curved portion of the skin portion 38.
  • the lower rear opening portion 42b extends essentially horizontally rearwardly.
  • this door assembly 54 is particularly adapted to close the forward opening portion 42a in a particularly convenient and effective manner so as to be compatible with the configuration and operating characteristics of the components described above.
  • This door assembly 54 comprises a door member 56 and a mounting device 58 by which the door member 56 is mounted for rotation from a first retracted position illustrated at 56a in Figure 6) to a second deployed position (illustrated at 56b in Figure 6).
  • the door member 56 is curved to match the general configuration of the forward skin portion 38.
  • the door member 56 comprises a middle forward portion 60, a downwardly and rearwardly curving lower portion 62, and an upwardly and rearwardly curving upper portion 64.
  • the perimeter portion of the door member 56 extends moderately beyond the edge openings 46 and 44 so as to fit against a perimeter portion 66 of the skin section 38, which perimeter portion 66 defines the opening portion 42a.
  • the mounting device 58 is essentially a spring loaded hinge assembly comprising a first arm 68 fixedy attached to the inner surface of the skin portion 38, and a second swing arm 70 fixedly attached to the inner surface of the lower portion 62 of the door member 56.
  • the hinge connection of the arms 68 and 70 is or may be conventional and is designated 72.
  • a spring member 74 has a middle coil portion 76 wrapped around the hinge portion 72, and two spring arms 78 and 80 reacting against the arms 68 and 70, respectively. The action of the spring member 74 is such that it urges the swing arm 70 and the door member 56 downwardly and forwardly to the deployed position at 56b where the door member 56 closes the front opening portion 42a.
  • the door assembly 54 is particularly arranged to function in the rather limited space which exists between the skin portion 38 and the web 52 of the front spar 50.
  • the axis of rotation 82 provided by the hinge mechanism 72 is arranged so that it extends upwardly and forwardly, so as to be generally positioned in (i.e. have substantial alignment components parallel to) a vertical plane which is generally parallel to a vertical plane through which the main track 18 moves between its retracted and deployed positions. Further, this axis of rotation 82 is spaced laterally in a spanwise direction from the plane of motion within which the main track 18 moves.
  • this axis of rotation 82 has a substantial component of alignment that is generally perpen- dicularto a plane occupied by an upper portion 84 of the forward skin section 38, the portion 84 being that part of the skin section 38 which the door 56 moves adjacent to and generally parallel with, in moving from its deployed position 56b to its retracted position 56a.
  • the axis of rotation 82 should have a substantial component of alignment generally perpendicular to the plane occupied by the upper skin portion 84, this being the skin portion which the door member 56 moves adjacent to as it moves to its deployed position 56a. Further, as indicated previously, the axis of rotation 82 should have a substantial-component of alignment which lie in a vertical plane which is generally parallel to a vertical plane in which the main track 18 moves in travelling between its retracted position to its deployed positions 14a or 14b.
  • the axis of rotation 82 could deviate to some extent from these alignment limitations, depending upon the geometry and configuration of the surrounding structure.
  • the present invention has been shown used with a track 18, it is to be understood that it could be used with other components where similar problems exist, such as a service connection (e.g. a telescoping tube) which would provide de- icing for the leading edge slat.
  • a service connection e.g. a telescoping tube
  • leading edge is, within the broader scope of the present invention, intended to refer to a trailing edge configuration where like problems may exist.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Specific Sealing Or Ventilating Devices For Doors And Windows (AREA)

Claims (8)

1. Tragfläche, umfassend einen Vorderhautabschnitt (12, 38), und eine Profilvorderkanteneinrichtung (14), die eine Reiseflugposition hat, in welcher sie den Vorderhautabschnitt abdeckt, und eine entfaltete Position, in welcher der Vorderhautabschnitt der Luftströmung ausgesetzt ist, wobei die Tragfläche eine spannweitenweise Achse, eine sehnenweise Achse und eine Vertikalachse hat, wobei die Tragfläche ein Verbindungsteil (18) hat, das mit der Profilvorderkanteneinrichtung verbunden ist, wobei der Vorderhautabschnitt eine vordere Öffnung (42) hat, durch welche sich das Verbindungsteil erstreckt, wobei Mittel (54, 56) zum Verschließen der Öffnung vorgesehen sind, wobei die Tragfläche dadurch gekennzeichnet ist, daß das Verbindungsteil (18) während der Bewegung der Profilvorderkanteneinrichtung (14) in ihre entfaltete Position eine generell quer zu der sehnenweisen Achse verlaufende Bewegungskomponente in der Öffnung (42) zu einer quer verlagerten Position hat, so daß ein Teil der Öffnung als ein freiliegender Vorderhautoffenbereich bleibt,
wobei die Mittel zum Schließen der Öffnung folgendes umfassen:
a. eine Tür (56), die eine Oberflächenkonfiguration hat, welche generell dem freiliegenden Vorderhautoffenbereich entspricht;
b. eine Drehgelenkbefestigungseinrichtung (58) mittels deren die Tür drehbar in der Profilvorderkantenstruktur zur Bewegung um eine Drehachse
(82)montiert ist, weiche eine wesentliche Ausrichtungskomponente generell senkrecht zu einem Teil des Vorderhautabschnitts benachbart dem freiliegenden Vorderhautoffenbereich hat, und eine wesentliche Ausrichtungskomponente parallel zu einer Bewegungsebene, durch welche das Verbindungsteil sich von seiner ersten Position zu seiner zweiten Position bewegt, wobei die drehende Befestigungseinrichtung derart ist, daß die Tür eine erste eingefahrene Position (56a) hat, in welcher die Tür von dem freiliegenden Vorderoberflächenoffenbereich entfernt und um die erwähnte Drehachse aus einer Position, die von dem Verbindungsteil in seiner eingefahrenen Position eingenommen wird, verlagert ist, und eine zweite entfaltete position (56b), in welcher die Tür in der erwähnten Bewegungsebene positioniert ist und wenigstens einen Teil des freiliegenden Vorderoberflächenoffenbereichs schließt;
c. Mittel (68, 70, 74, 76, 78, 80) zum Bewirken, daß sich die Tür zwischen ihrer eingefahrenen und entfalteten position bewegt.
2. Tragfläche nach Anspruch 1, dadurch gekennzeichnet, daß die Mittel zum Bewirken, daß sich die Tür (56) bewegt, Federmittel (68, 70, 74, 76, 78, 80) umfassen, die operativ mit der Tür zum Bewegen der Tür nach deren entfalteter Position zu, verbunden sind.
3. Tragfläche nach Anspruch 1 oder 2, dadurch gekennzeichnet, daß die Tür (56) einen Kontaktteil hat, und daß das Verbindungsteil (18) beim Bewegen von seiner entfalteten in seine eingefahrene Position mit dem Kontaktteil in Eingriff tritt, um die Tür in ihre eingefahrene Position zu bewegen.
4. Tragfläche nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß sich das Verbindungsteil (18) beim Bewegen zwischen seiner eingefahrenen zu seiner entfalteten Position nach vorwärts und auch abwärts bewegt, so daß es den freiliegenden Vorderoberflächenoffenbereich über dem Verbindungsteil in seiner entfalteten Position verläßt, worin der Vorderhautabschnitt an dem Ort der erwähnten Öffnung (42) eine aufwärtige und rückwärtige Schräge hat, und die erwähnte Drehachse (82) so ausgerichtet ist, daß sich die Tür (56) in einer aufwärtigen und rückwärtigen Richtung benachbart dem Vorderhautabschnitt benachbart der Öffnung bewegt.
5. Tragfläche nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die Profilvorderkanteneinrichtung einen Profilvorderkantenvorflügel (14) umfaßt, welcher sich so nach abwärts und vorwärts bewegt, so daß er mit dem Vorderoberflächenabschnitt einen Schlitz bildet, durch welchen Luft in einer aufwärtigen Richtung und dann über eine obere Oberfläche der Tragfläche strömt.
6. Tragfläche nach Anspruch 5, dadurch gekennzeichnet, daß das Verbindungsteil ein Schienenteil (18) umfaßt, das sich in einer abwärtigen und vorwärtigen Richtung zum Lokalisieren des Vorflügels (14) in seiner entfalteten Position bewegt.
7. Tragfläche nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die erwähnten Federmittel einen ersten Befestigungsarm (68) umfassen, der mit der Profilvorderkantenstruktur verbunden-ist, und einen zweiten Befestigungsarm (70), der drehbar mit dem ersten- Befestigungsarm verbunden und mit der Tür (56) verbunden ist, wobei die Federmittel weiter ein Federteil (74) umfassen, das eine operative Verbindung zwischen dem erwähnten ersten und zweiten Arm bildet, um die Tür in ihre entfaltete Position zu drängen.
8. Tragfläche nach Anspruch 7, dadurch gekennzeichnet, daß die erwähnte Drehachse (82) benachbart der Tür (56) an einem Ort lokalisiert ist, welcher benachbart einem unteren Seitenteil der Tür ist, und zwar in einer Weise, daß die Tür, wenn sie sich aus ihrer entfalteten Position bewegt, primär eine Aufwärtsbewegung hat, wenn sich die Tür anfänglich aus ihrer entfalteten Position bewegt.
EP85201286A 1984-12-31 1985-08-08 Abschlussvorrichtung für eine Flügelfläche Expired EP0188823B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US687929 1984-12-31
US06/687,929 US4640477A (en) 1984-12-31 1984-12-31 Closing device for an airfoil

Publications (2)

Publication Number Publication Date
EP0188823A1 EP0188823A1 (de) 1986-07-30
EP0188823B1 true EP0188823B1 (de) 1988-10-19

Family

ID=24762434

Family Applications (1)

Application Number Title Priority Date Filing Date
EP85201286A Expired EP0188823B1 (de) 1984-12-31 1985-08-08 Abschlussvorrichtung für eine Flügelfläche

Country Status (3)

Country Link
US (1) US4640477A (de)
EP (1) EP0188823B1 (de)
DE (1) DE3565660D1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11845550B2 (en) 2019-02-28 2023-12-19 Airbus Operations Gmbh Wing leading-edge device and a wing having such a wing leading-edge device

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2204538B (en) * 1987-05-06 1990-12-12 British Aerospace Wing leading edge arrangements for aircraft
GB8729655D0 (en) * 1987-12-19 1988-02-03 British Aerospace Wing leading edge arrangements for aircraft
US4838502A (en) * 1988-03-16 1989-06-13 The Boeing Company Resiliently deployable fairing for sealing an airframe cavity
GB8910654D0 (en) * 1989-05-09 1989-06-21 British Aerospace Flexible closing device for a wing leading edge
GB9607707D0 (en) * 1996-04-13 1996-06-19 Broadbent Michael C A self-sealing parallelogram slat mechanism
US6015117A (en) * 1996-04-13 2000-01-18 Broadbent; Michael C Variable camber wing mechanism
US5927656A (en) * 1996-06-26 1999-07-27 The Boeing Company Wing leading edge flap and method therefor
DE19925560B4 (de) 1999-06-04 2004-04-22 Deutsches Zentrum für Luft- und Raumfahrt e.V. Zusatzflügel für Hauptflügel von Flugzeugen
GB0114634D0 (en) 2001-06-15 2001-08-08 Broadbent Michael C Contiguous variable camber device
US7249735B2 (en) * 2005-06-30 2007-07-31 The Boeing Company Translating conduit apparatus for an airplane or equipment
GB0722425D0 (en) * 2007-11-15 2007-12-27 Airbus Uk Ltd Slat support funk plate
GB201008773D0 (en) * 2010-05-26 2010-07-14 Airbus Uk Ltd Aircraft slat assembly
US8622350B1 (en) * 2011-11-14 2014-01-07 The Boeing Company Compound leading edge device for aircraft
US9296464B1 (en) * 2014-11-12 2016-03-29 The Boeing Company Aircraft and associated door member biasing assembly and method
GB2533311A (en) * 2014-12-15 2016-06-22 Airbus Operations Ltd A track container
US9937999B2 (en) * 2015-06-01 2018-04-10 Northrop Grumman Systems Corporation Deployable propeller
US11192625B2 (en) 2016-06-17 2021-12-07 Bombardier Inc. Panels for obstructing air flow through apertures in an aircraft wing
US11713106B2 (en) * 2019-03-26 2023-08-01 Embraer S.A. Articulated cover assembly for wing leading edge slat telescopic tube duct

Family Cites Families (10)

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Publication number Priority date Publication date Assignee Title
US2381680A (en) * 1940-11-12 1945-08-07 Frank R Maxwell Airplane and control device therefor
US2381679A (en) * 1940-11-12 1945-08-07 Frank R Maxwell Airplane and control device therefor
FR1011175A (fr) * 1948-12-20 1952-06-19 Onera (Off Nat Aerospatiale) Perfectionnement aux ailes d'avions
GB1070723A (en) * 1963-01-16 1967-06-01 Dehavilland Aircraft Improvements in or relating to aircraft
US3680815A (en) * 1967-06-14 1972-08-01 Avions Marcel Dassult Obturator for openings formed in aircraft fairings
US3968946A (en) * 1975-03-31 1976-07-13 The Boeing Company Extendable aerodynamic fairing
US4042191A (en) * 1976-05-03 1977-08-16 The Boeing Company Slot seal for leading edge flap
US4189121A (en) * 1978-01-23 1980-02-19 Boeing Commercial Airplane Company Variable twist leading edge flap
GB1572004A (en) * 1978-03-30 1980-07-23 Hawker Siddeley Aviation Ltd Aircraft wings
US4360176A (en) * 1979-11-05 1982-11-23 The Boeing Company Wing leading edge slat

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11845550B2 (en) 2019-02-28 2023-12-19 Airbus Operations Gmbh Wing leading-edge device and a wing having such a wing leading-edge device

Also Published As

Publication number Publication date
EP0188823A1 (de) 1986-07-30
US4640477A (en) 1987-02-03
DE3565660D1 (en) 1988-11-24

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